Metallic stator seal

The present application and the resultant patent relate generally to gas turbine engines and more particularly relate to stator seals having a number of metallic layers and cloth layers for reduced leakage.

Leakage of hot combustion gases and/or cooling flows between turbine components generally causes reduced power output and lower efficiency. For example, the hot combustion gases may be contained within the turbine by providing pressurized compressor air around the hot gas path. Leakage of high pressure cooling flows into the hot gas path thus may lead to detrimental parasitic losses. Overall efficiency thus may be improved by blocking the leakage locations while providing cooling flow only as required.

For example, current gas turbines may use cloth seals between adjacent stator components to limit the leakage of cooling flows therebetween. Such cloth seals may have a woven wire mesh cloth layer wrapped around a metal shim with a curved “shepherds hook” on either side. Manufacturing variations, however, involved in creating the shepherds hook and the overall cloth seal may impact the leakage rate therethrough. Even lower leakage rates may be achieved by using thin metal shims between the stator components. To date, however, the use of such thin metal shims in heavy duty gas turbines has not been feasible given concerns with robustness as well as manufacture and assembly issues with such seals.

There is thus a desire for an improved seal assembly for use between stator components and other components in a heavy duty gas turbine engine. Such a seal assembly may be substantially temperature resistant, wear resistant, and flexible so as to provide adequate sealing with a robust component lifetime.

The present application and the resultant patent thus provide a seal assembly for a turbine. The seal assembly may include a first metal shim, a second metal shim, and one or more flexible layers positioned between the first metal shim and the second metal shim.

The present application and the resultant patent further may provide a turbine. The turbine may include a first stator, a second stator, and a seal assembly positioned between the first stator and the second stator. The seal assembly may include a pair of metal shims surrounding one or more cloth layers.

The present application and the resultant patent further may provide a turbine. The turbine may include a first stator, a second stator, and a seal assembly positioned between the first stator and the second stator. The seal assembly may include a first metal shim in a top position, a second metal shim in a bottom position, and a first woven wire mesh and a second woven wire mesh in a middle position.

These and other features and improvements of the present application and the resultant patent will become apparent to one of ordinary skill in the art upon review of the following detailed description when taken in conjunction with the several drawings and the appended claims.

FIG. 1 is a schematic view of a gas turbine engine showing a compressor, a combustor, and a turbine.

FIG. 2 is a partial side view of a turbine.

FIG. 3 is a side cross-sectional view of a stator seal assembly as may be described herein.

Referring now to the drawings, in which like numerals refer to like elements throughout the several views, FIG. 1 shows a schematic view of gas turbine engine 10 as may be used herein. The gas turbine engine 10 may include a compressor 15 . The compressor 15 compresses an incoming flow of air 20 . The compressor 15 delivers the compressed flow of air 20 to a combustor 25 . The combustor 25 mixes the compressed flow of air 20 with a pressurized flow of fuel 30 and ignites the mixture to create a flow of combustion gases 35 . Although only a single combustor 25 is shown, the gas turbine engine 10 may include any number of combustors 25 . The flow of combustion gases 35 is in turn delivered to a turbine 40 . The flow of combustion gases 35 drives the turbine 40 so as to produce mechanical work. The mechanical work produced in the turbine 40 drives the compressor 15 via a shaft 45 and an external load 50 such as an electrical generator and the like.

The gas turbine engine 10 may use natural gas, various types of syngas, and/or other types of fuels. The gas turbine engine 10 may be any one of a number of different gas turbine engines offered by General Electric Company of Schenectady, N.Y. including, but not limited to, those such as a 7 or a 9 series heavy duty gas turbine engine and the like. The gas turbine engine 10 may have different configurations and may use other types of components. Other types of gas turbine engines also may be used herein. Multiple gas turbine engines, other types of turbines, and other types of power generation equipment also may be used herein together.

FIG. 2 shows a portion of an example of the turbine 40 . Generally described, the turbine 40 may include a first stage nozzle 55 and a first stage bucket 60 in a first stage 65 . Also shown is a second stage nozzle 70 of a second stage 75 . Any number of stages may be used herein. The second stage nozzle 70 may be positioned about a diaphragm 80 . The nozzle 70 and the diaphragm 80 form part of a stator 85 . Any number of stators 85 may be positioned circumferentially about an axis 90 in each of the stages. A stator seal 95 may be positioned between adjacent stators 85 about the diaphragm 80 or elsewhere. The stator seals 95 prevent the leakage of the cooling air flows 20 from the compressor therethrough. Other components and other configurations may be used herein. For example, other components may include shrouds, casings, nozzles, transition pieces, and the like.

FIG. 3 shows portions of an example of a turbine 100 as may be described herein. Specifically, a first turbine component 110 and a second turbine component 120 are shown. The turbine components 110 , 120 may be a first nozzle 130 of a first stator 135 and a second nozzle 140 of a second stator 150 as described above or any other pair of adjacent turbine components. Any number or type of turbine components may be used herein.

The turbine 100 may include a seal assembly 160 positioned between each pair of the turbine components 110 , 120 . The seal assembly 160 may extend from a first seal slot 170 in the first turbine component 110 to a second seal slot 180 in the second turbine component 120 . The seal slots 170 , 180 may have any size, shape, or configuration. The seal assembly 160 blocks a gap 190 between the components 110 , 120 so as to prevent the escape of the cooling air flows 20 therethrough and the like. Other locations may be used herein.

The seal assembly 160 may include a pair of metal shims: a first metal shim 200 and a second metal shim 210 . The metal shims 200 , 210 may be relatively thin but solid metal stock. The metal shims 200 , 210 may be made out of a high temperature resistant material such as stainless steel or a nickel based alloy Other types of materials may be used herein. Additional metal shim layers also may be used.

The seal assembly 160 also may include a pair of flexible cloth layers: a first cloth layer 220 and a second cloth layer 230 . Any number of the flexible cloth layers 220 , 230 may be used herein. The flexible cloth layers 220 , 230 may be made out of a woven wire mesh 240 or any flexible high temperature material. For example, metal foam, a hollow box-type shim, or even additional welded shim layers and the like may be used. The first metal shim 200 may have a top position 250 , the second metal shim 210 may have a bottom position 260 , and the flexible cloth layers 220 , 230 may have a middle position 270 . (The terms “top”, “bottom”, “middle”, reflect relative, as opposed to absolute, positions.) The metal shims 200 , 210 and the flexible cloth layers 220 , 230 may be coupled via high temperature adhesives, high strength fasteners, welding, and other types of conventional fastening means. The seal assembly 160 and the components thereof may have any desired size, shape, or configuration. Additional non-metallic filler materials also may be used so as to add thickness therein without impacting on overall flexibility.

The use of the metal shims 200 , 210 in both the top position 250 and the bottom position 260 thus allows the seal assembly 160 to be reversible, i.e., the seal assembly 160 may be installed with either position on the load surface in the seal slots 170 , 180 of the turbine components 110 , 120 . The metal shim layers 200 , 210 act as the seal surface so as to provide low leakage rates therethrough. The metal shim 200 in the top position 250 also serves as a supplemental leakage barrier in the event that the metal shim 210 in the bottom position 260 is somehow compromised. The flexible cloth layers 220 , 230 provide thickness to the seal assembly 160 without substantially increasing overall stiffness. The flexible cloth layers 220 , 230 also mitigate potential assembly or maintenance concerns.

The seal assembly 160 thus provides low leakage rate similar to that possible with thin metal shim seals while eliminating the manufacturing, assembly, and robustness concerns when applied to a heavy duty gas turbine. Moreover, the seal assembly 160 may be less susceptible to manufacturing, variations as compared to existing cloth seals. The seal assembly 160 thus reduces leakage with low manufacturing and operational risks. The seal assembly 160 may be original equipment or part of a retrofit.

It should be apparent that the foregoing relates only to certain embodiments of the present application and the resultant patent. Numerous changes and modifications may be made herein by one of ordinary skill in the art without departing from the general spirit and scope of the invention as defined by the following claims and the equivalents thereof.